KR20180078308A - Lubricant flow separation device and exhaust gas turbocharger with such device - Google Patents

Abstract

The apparatus according to the invention is used to separate the lubricating oil flow in a lubricating oil receiving bearing housing 10 of an exhaust turbo supercharger with an axial turbine, wherein the exhaust turbo supercharger is connected to the turbine housing through the bearing housing, , Two radial bearings (12, 13) arranged along the shaft and an axial bearing (14) of a shaft located between these radial bearings. The apparatus includes one or more wall protrusions 40 which protrude radially inwardly into the gap 17 of the bearing housing from the inner wall of the bearing housing in the direction of the shaft. The gap 17 extends between the axial bearing 14 and the turbine-side radial bearing 13 and tapers gradually toward the turbine side in the axial direction. Lubricating oil, which is carried from the axial bearing 14 and encircles the axial bearing, strikes against the wall section of the bearing housing is deflected by the wall projection 40 and guided in the space direction under the shaft. As a result, a large amount of lubricating oil transferred from the axial bearing 14 flows toward the seat of the turbine side radial bearing 13, and there is a small amount of the lubricating oil transferred from the steep taper position of the gap 17 through the turbine side radial bearing Is prevented. The invention also relates to an exhaust gas turbocharger having such an arrangement.

Description

Lubricant flow separation device and exhaust gas turbocharger with such device

The present invention relates to the field of exhaust gas turbochargers.

The present invention relates to a separator for separating lubricant flow in a bearing housing of an exhaust gas turbocharger housing a lubricating oil and to an exhaust gas turbocharger having such an apparatus.

The exhaust turbo supercharger uses the exhaust gas of the internal combustion engine to compress the combustion air to be supplied to the internal combustion engine. Such precompression or filling of the combustion air increases the charge level and, in addition, the in-cylinder fuel mixture of the engine, which in turn can significantly increase the efficiency of the engine. The exhaust gas turbocharger used in this connection consists essentially of fixed housing parts such as a rotor, consisting of a turbine wheel, a compressor wheel and a shaft connecting these components, a bearing and a turbine housing, a compressor housing and a bearing housing for receiving the bearing, .

The bearings of the exhaust gas turbocharger located in the bearing housing basically comprise two radial bearings and one axial bearing, each of which is supplied with lubricating oil through dedicated lines. The lubrication oil performs not only the lubrication function but also the cooling function for the operating temperature in the turbine housing which can reach up to 600 ° C to 1000 ° C depending on the operating point. To prevent lubricant from entering the housing of an adjacent compressor or turbine, the bearing housing includes suitable seals such as, for example, a piston ring and oil collection systems. The lubricant collected in the oil collection systems is guided to the oil outlet located below the shaft by gravity.

The turbine of the exhaust gas turbocharger may be provided as a radial turbine or an axial turbine, in which case the exhaust gas flow is actually radially introduced from the outside in relation to the rotor axis and guided in the direction of the turbine wheel. In the case of an axial turbine, the exhaust gas of the engine driving this turbine flows in the axial direction around the turbine. The exhaust gas is likewise discharged in the same axial direction through the gas outlet of the turbine housing located behind the turbine wheel of the axial turbine in the gas flow direction. A corresponding section of the gas outlet extending in the axial direction surrounds a portion of the bearing housing connected to the turbine housing. The radial spacing of the shaft and the turbine housing portion as described above extending axially is predetermined by the radius of the turbine wheel. Because of this predetermined radial spacing, the bearing housing area adjacent to the turbine housing has less space available than the compressor housing bearing housing area. Thus, the portion of the bearing housing adjacent to the turbine housing tapers along its radially tapered direction toward the turbine. Such tapering affects the space ratio in relation to the possibility of discharge of bearings located in such bearing housing areas as well as of lubricating oil carried through the bearings.

The proportion of lubricant delivered through the axial bearing exceeds the amount transferred through the radial bearing. The lubricant delivered through the radial bearing is first of all radially discharged from the radial bearing in an axial direction relative to the shaft. On the other hand, most of the lubricating oil delivered through the axial bearings is radially outwardly thrown at high speeds to hit the walls of the bearing housing surrounding the circumference. At the same time, the arrangement of the axial bearings relative to the radial bearings and, in particular, the space ratio in relation to the axial bearings influence the oil discharge potential.

In the following, the arrangement of the bearings along the shaft of the turbocharger with an axial turbine should be referred to, in which case the compressor side radial bearing is preceded by an axial bearing followed by the turbine side radial bearing. In the case of different arrangements of bearings along the shaft, for example in situations with axial bearings disposed on the compressor side and subsequent radial bearings positioned along the shaft in the turbine direction, the following problem of the two lubricant flows affected Does not occur in the above-described manner.

In the following, the reference system is referred to when the terms " upper (upper) "and" lower (= lower) " are used in the following, in which the turbocharger is in a horizontal plane, Lt; / RTI > In this context, the terms "above" and "below" should be understood to relate to a vertical line, ie, a direction given by gravity. The actual alignment of the turbocharger during installation may differ from the horizontal alignment described above.

A schematic structure of a prior art turbocharger having an axial turbine 3 and an axial bearing 14 disposed between a compressor side radial bearing 12 and a turbine side radial bearing 13 is disclosed in FIG. have. The lubricant transferred through the axial bearing 14 to the space located between the axial bearing 14 and the turbine side radial bearing 13 on the shaft 11 in relation to the vertical line is mainly radial bearing In the direction of the wall of the bearing housing 10 which limits the area of the bearing housing 10. The lubricating oil travels along the walls in the turbine lateral direction from this position. At this position, the lubricating oil impinges on the seat of the turbine side radial bearing 13, and is finally moved by gravity and flows to the tapered region below the turbine side radial bearing seat. The drain or outlet 16 of the lubricant flow is typically located in the region beneath the compressor-side radial bearing 12. Due to the shape of the inner wall of the bearing housing 10 that widens in the direction of the compressor 2, i.e., with increasing distance from the shaft, the lubricant reaching below the axial bearing 14 and the turbine side radial bearing 13 Is again moved by gravity and is guided in the direction of the discharge port (16).

A large amount of lubricating oil conveyed from the axial bearing 14 in the direction of the turbine side radial bearing 13 forms a curtain of lubricating oil in front of the sheet of the turbine side radial bearing. This lubricating oil is moved by gravity from the housing walls in this position to the area under the shaft and is guided along the housing walls which are finally expanded toward the outlet 16. [ The lubricating oil conveyed from the radial bearing 13 on the turbine side does not flow in the direction of the discharge port 16 due to the flow of the lubricating oil. This causes the lubricating oil to stagnate on the turbine side of the bearing housing and leak to the turbine housing. Due to the high process temperature on the turbine side, coking can occur if the lubricating oil stagnates in the region of the bearing housing directly adjacent to the turbine housing.

As described in Claims 1 to 7, the object of the present invention is to prevent lube oil stagnation on the sheet of the turbine side radial bearing in the bearing housing of the exhaust gas turbocharger housing the lubricating oil, Which is capable of improving the lubricant discharge on the engine. The invention also relates to an exhaust gas turbocharger as defined in claim 8, having said apparatus.

In connection with the present invention, oil in a bearing housing that performs a lubrication function is applied. Where the terms oil or oil flow are used below, they should be understood to have the same meaning as the lubricant or lubricant flow.

In the device according to the invention there is provided at least one wall protrusion radially projecting into the gap from the inner wall of the bearing housing in at least one gap region between the axial bearing and the turbine side radial bearing located on the shaft in relation to the vertical line. The one or more wall protrusions divide the gap into at least an area adjacent to the axial bearing and an area adjacent to the turbine side radial bearing in an area above the shaft at least in relation to gravity. The oil flow of the axial bearing and the turbine side radial bearing can be separated by the at least one wall projection so that the mutual influence of the oils can be prevented. The oil flow of the axial bearing is biased directly into the area of the bearing housing, where the area of the bearing housing is offset from the turbine side radial bearing in the direction of the axial bearing. This can reduce the piling or accumulation of the oil flow in the turbine side radial bearing due to the oil flow of the axial bearing and can improve the discharge of the oil flow in the turbine side radial bearing in the direction of the oil outlet. Thus, in particular, the efficiency of the turbine side shaft seal disposed on the turbine side of the turbine side radial bearing is also increased.

In order to further increase the efficiency of the turbine side shaft seal by improved oil drainage, additional axially extending exhaust grooves may be provided in combination with the aforementioned wall protrusion. These discharge grooves can be disposed on the shaft axis with respect to gravity, wherein the bearing housing wall surrounds the axial extension of the turbine side radial bearing. Through such discharge grooves, a gap between the axial bearing and the turbine side radial bearing and a space on the turbine side of the turbine side radial bearing are made. The discharge grooves are used as additional discharge surfaces while the discharge surface conveys part of the lubricant transferred through the turbine side radial bearing from the space on the turbine side of the radial bearing space in the direction of the gap between the axial bearing and the turbine side radial bearing do. The discharge grooves thus enable further division of the oil flow transferred through the turbine side radial bearings. The oil flow from the discharge grooves may be separated from the oil flow of the axial bearing in particular by the wall projection projecting into the gap between the axial bearing and the turbine side radial bearing and not be blocked by the axial bearing.

In the following, an embodiment of an oil flow separation apparatus according to the present invention is shown and described in more detail with reference to the drawings. The same reference numerals are provided for the same elements in the figures.

1 is a schematic diagram of a prior art exhaust turbo supercharger with an axial turbine, in which case the housing of the turbine is cut along the rotor axis,
Fig. 2 is a schematic cross-sectional view of bearing housing portions enclosing the circumference of the bearing arrangement and the wall projection for separating the lubricant flow of the axial bearing and the turbine side radial bearing,
3 is a schematic cross-sectional view with an additional wall protrusion for separating the lubricant flow of the axial bearing and turbine side radial bearing, and
Fig. 4 is an isometric sectional view of the region of the bearing housing and the turbine side radial bearing surrounding the turbine side radial bearing in the radial direction.

1 shows a prior art exhaust turbocharger with a compressor housing 2 as a fixed housing component, a compressor 2 with a bearing housing 10 and a turbine housing, a bearing 1 and an axial turbine 3, Figure 5 shows a schematic cross section of a supercharger. The compressor wheel 21, the turbine wheel 31 and the shaft 11 connecting the compressor wheel to the turbine wheel are components of the rotor of the exhaust turbocharger. The shaft 11 is guided from the compressor housing 20 which houses the compressor wheel 21 into the turbine housing 30 which receives the turbine wheel 31 through the bearing housing 10. A filter silencer 22 is also shown as an optional part of the exhaust gas turbocharger, which is connected to the compressor housing and is used to attenuate significant noise at the compressor wheel position during operation of the exhaust turbocharger.

With regard to rotor penetration, sealing devices are located in the transition areas between the three fixed housing components mentioned above. These sealing devices must prevent the flow of mass from the compressor or turbine side into the bearing housing due to the relatively high process pressure that sometimes exists at the compressor or turbine side. In order to seal the bearing housing against the mass flow of the compressor or turbine side, a sealing air system can also be used in the bearing housing. Furthermore, the sealing devices must prevent lubricant from coming out of the bearing housing and out into the turbine or compressor. In this case, the lubricant is used for lubrication of the bearings of the rotor but can also be used for cooling the high operating temperature of the turbine side.

The bearing of the shaft 11 in the bearing housing 10 shown in Figure 1 includes a compressor side radial bearing 12, a turbine side radial bearing 13 and an axial bearing 14 disposed between the two radial bearings Respectively. These bearings are supplied with lubricating oil through oil feed lines (15). The supplied lubricating oil finally reaches the internal space area of the bearing housing, which is located below the shaft with respect to the vertical line by gravity. In this region, an oil discharge port 16 is disposed under the compressor-side radial bearing 12. [

On the turbine side, the turbocharger includes a gas inlet housing 301 and a gas outlet housing 302 of a turbine 3 designed as an axial turbine. The directions of the exhaust gas flowing into and out of the axial turbine 3 are shown by arrows corresponding to FIG. The gas outlet channel defined by the gas outlet housing has a section 303 that extends axially substantially immediately behind the turbine wheel in the gas flow direction. This section fully surrounds a portion of the bearing housing and causes the radial cross section of the bearing housing to taper in an axial direction from the compressor side to the turbine side. As a result, a corresponding taper of the gap 17 between the shaft 11 and the inner wall of the bearing housing 10 in the region of the axial bearing 14 and the turbine side radial bearing 13 occurs.

Fig. 2 schematically shows an embodiment of the present invention. 2, there is shown a cross-sectional view of a portion of a bearing housing 10 that includes a perforated shaft 11, a compressor-side radial bearing 12, a turbine side radial bearing 13, and an axial bearing 14 . The gas outlet housing 302 of the turbine restricts the bearing housing 10 in the radially extending portion of the region shown, so that the gap 17 in particular becomes tapered in the axial direction towards the turbine in the bearing housing. According to one embodiment of the present invention, a wall projection 40 is provided, which protrudes radially inwardly from the bearing housing wall into the gap 17. The wall protrusion 40 may be formed in the shape of a partial ring in the region of the gap 17 above the shaft at least in relation to the vertical line, the partial ring correspondingly surrounding the shaft in the form of a partial ring. As measured in relation to the vertical line, the partial rings may have, for example, angles ranging from + 35 ° to -35 °, + 45 ° to -45 ° or + 55 ° to -55 °, And may extend in a plane perpendicular to the axis A.

An additional option (not shown) for the shape of the wall protrusion 40 is a wall protrusion completely surrounding the shaft, i.e., an annular wall protrusion that is fully guided about the shaft. In this case, the annular wall projection is connected to the bearing housing walls in the region of the gap 17 located above the shaft 11. The annular wall projection in the region of the gap 17 located below the shaft 11 must prevent the oil flow flowing from the turbine side radial bearing 13 and flowing in the oil discharge direction from under the compressor side radial bearing 12 do. To this end, at least in the region under the shaft 11, a gap may be provided between the outer edge of the annular wall projection and the wall portions of the bearing housing disposed under the outer edge of the annular wall projection in relation to gravity. In other words, there should be at least no continuous connections between the wall protrusions and the bearing housing walls in the area below the shaft. In particular, in the area beneath the wall protrusion and in relation to gravity, at the point of the deepest bearing housing walls, a gap must be provided between the bearing housing walls and the annular wall protrusion. Unrestricted discharge of the oil flow from the turbine side radial bearing 13 toward the oil discharge direction can be ensured. Subsequently, it may also be desirable that the area of the annular wall projection located below the shaft 11 be inclined in the compressor lateral direction with respect to the vertical line. In this case, the oil delivered from the axial turbine and striking the annular wall protrusion has already been directed in the oil discharge direction through the inclined portion of the wall protrusion. The oil flow flowing in the oil discharge direction from the inclined area of the wall projection can provide a favorable suction effect on the oil flow from the turbine side radial bearing. This suction effect can lead to an improved further discharge of oil flowing through the turbine side radial bearing 13 in the discharge direction.

Between the surface F of the wall protrusion 40 facing the shaft and the shaft 11 is provided a radial gap such that the rotational behavior of the shaft 11 is not affected by the wall protrusion 40. [ The wall protrusion 40 having the above-described characteristics ensures that most of the lubricating oil fed through the axial bearing 14 in the gap 17 on the shaft 11 reaches the seat of the turbine side radial bearing 13 Can be prevented. Instead, the lubricating oil can be discharged by gravity at the end face 41 of the wall projection 40 facing the axial bearing 14. [ As a result, the lubricating oil can flow directly into the area of the gap 17 below the shaft, where the area of the gap has a larger radial cross section compared to the area which is considerably tapered on the seat of the turbine side radial bearing 13. In this case, the lubricant flow delivered through the turbine side radial bearing 13 no longer meets the much larger volume of oil flow on the side of the axial bearing 14 directly on the turbine side radial bearing seat. This advantageously achieves separation of the two lubricant streams. This separation results in better lubricant discharge towards the oil outlet and avoids oil-blocking related leakage at the turbine side seal portion of the bearing housing.

In order to further improve the discharge of the lubricating oil conveyed through the axial bearing 14 at the end face 41 of the wall projection 40, the wall projection or end face 41 may have a particularly smooth or coated surface have.

Figure 3 shows a further embodiment according to the invention. The cutting portion of the bearing housing shown in Fig. 3 corresponds to the cutting portion of the bearing housing shown in Fig. In addition to the wall projection 40 shown in Fig. 2, an additional wall projection 42 is shown which is offset axially relative to the wall projection 14 towards the axial bearing 14 Respectively. Likewise, the second wall projection 42 may also be designed as a partial ring at least partially surrounding the shaft and projecting radially into the gap 17. The angular extent in which the partial ring-shaped second wall projection extends in a plane perpendicular to the axis A of the shaft is such that the first partial ring-shaped wall projection 40 extends in an angular range extending in a corresponding parallel plane Can be corresponding. However, the angular range over which the second wall protrusion 42 extends may be arranged in such a manner that the first wall protrusion is offset with respect to the angular range in which the first wall protrusion extends. In addition, the first wall protrusion 40 and the second wall protrusion 42 can be formed in the form of a circular ring segment which is stopped in a certain angular range. For example, the second wall projection 40 may be formed in a plane perpendicular to the axis A of the shaft 11, measured from a vertical line between -45 degrees and 45 degrees, Cover. The first wall protrusion may be formed in the form of an interrupted circular ring segment having two partial sections. The two partial sections are elongated in an angular range of, for example, 30 ° to 80 ° and -80 ° to -30 ° in a plane perpendicular to the axis A of the shaft 11 from vertical when measured from a vertical line . Thus, each of the two section sections covers an angular range of 50 [deg.] In each case. In addition, one of the two wall protrusions may be provided in the above-described annular shape, that is, in a completely enclosed form of the shaft. Further, two wall protrusions may be given as annular wall protrusions. With this configuration of the first wall protrusion and the second wall protrusion as described below, the amount of lubricant transferred from the axial bearing can be further divided.

The radial distance between the shaft 11 and the face of the second wall protrusion 42 facing this shaft can be selected to be greater than the corresponding gap in the case of the first wall protrusion 40 as shown in Figure 3 have. The lubricant which is delivered from the axial bearing 14 by the arrangement of the two wall protrusions as described above and which is drawn in the wall portions of the bearing housing above the axis A of the shaft 11 with respect to the vertical line, And strikes against the wall protrusion 42 and flows at this position. A portion of this oil is dropped onto the shaft and the result is also again radially directed to the wall of the gap 17. In particular, this oil is also drawn to the wall portions between the second wall protrusions 42 and the first wall protrusions 40 that project radially into the gap 17. This oil may flow into the portion of the gap 17 below the shaft at the discharge surface 41 of the first wall projection. In this case, the radial distance between the shaft and the face F of the first wall projection 40 facing such a shaft is such that the oil dripped from the discharge surface 41 into the shaft is in a gap (not shown) adjacent to the turbine side radial bearing 14 To be able to be thrown into the region 172 of FIG.

By inserting the second wall protrusion 42 in addition to the first wall protrusion 40, further division of the lubricant carried through the axial bearing can be achieved. This lubricant flow splitting by an axial bearing may be further improved by a suitable combination of configurations of the first and second wall protrusions, as the case may be. This can be done, for example, by a combination of the two wall protrusions described above, wherein the first or second wall protrusion is designed in the form of an interrupted circular ring segment having two partial sections.

The end face 43 of the second wall protrusion 42 may have a particularly smooth or coated surface such as in the case of the end wall 41 of the first wall protrusion 40 to enable improved lubricant discharge do.

3, a total of three portions of this gap 17 in the region of the gap 17 over at least the shaft 11 through the first wall protrusion 40 and the second wall protrusion 42, Regions are separated from each other. The axial extension of the first partial region 171 of the gap 17 is limited by the axial bearing 14 and the second wall projection 42. [ The axial extension of the second partial region 172 of the gap is limited by the first wall projection 40 and the seat of the turbine side radial bearing 13. [ Finally, the limitation of the axial extension of the third partial region 173 is given by the first and second wall protrusions.

With regard to one of the embodiments of the present invention described with reference to Figures 2 and 3, a configuration of the bearing housing on the seat of the turbine side radial bearing 13 as shown in Figure 4 may additionally be provided . Figure 4 shows a schematic isometric cross-sectional view of a turbine side radial bearing 13 having a portion of the bearing housing 101 surrounding it, as viewed from the turbine side. In the bearing housing 101 above the shaft A of the shaft is located at least one discharge groove 50 extending substantially axially with respect to the axis. The discharge groove 50 provides a fluid connection for lubricant flow between the space adjacent the turbine side in the turbine side radial bearing seat and the partial region 172 of the gap 17. In particular, two discharge grooves 50 are shown in Fig. One of the two discharge grooves 50 shown in this case is arranged on the shaft A of the shaft in relation to gravity and the other one of the two discharge grooves 50 is arranged on the axis A of the shaft in relation to gravity, Respectively. The discharge grooves 50 are arranged in a bearing housing area 101 formed as a ring surrounding the turbine side radial bearing 13. [ When measured from a vertical line, the discharge grooves are in the plane perpendicular to the axis A of the shaft in the range of 25 DEG to 70 DEG or -25 DEG to -70 DEG and 115 DEG to 160 DEG or -115 DEG to -160 DEG Lt; / RTI > In particular, in addition to the two illustrated discharge grooves, additional discharge grooves can be disposed in the bearing housing area 101. [ For example, it is also possible that the discharge groove 50 is disposed only in the bearing housing area 101 located on the shaft A of the shaft, or the discharge groove 50 is disposed only in the bearing housing area located below the shaft A .

(Not shown) of one or more grooves 50 towards the gap 172 to facilitate discharge of the lubricating oil by gravity through the discharge groove in the direction of the partial region 172 of the gap 17. [ May be provided. The space adjacent to the turbine side of the turbine side radial bearing 13 in the region of the discharge grooves can be further extended in the axial and radial directions to facilitate the inflow of the lubricating oil toward the discharge grooves 50. [

As shown in FIG. 3, in the first and second wall protrusions 40 and 42, a partial area 172 of the gap 17 between the turbine side radial bearing 13 and the first wall protrusion 40 May be provided by the discharge groove 50 as well. In this case, the second discharge groove 50 can also be provided with discharge of lubricating oil into the partial region 173 between the first and second wall projection portions.

1: Bearings
10: Bearing housing
11: Shaft
12: Compressor side radial bearing
13: Turbine side radial bearing
101: Bearing housing on the seat of turbine side radial bearing
14: Axial bearing
15: Oil supply line
16: Oil outlet
17: Clearance
171: First partial area of the separated / axial bearing side clearance
172: second partial area of the separated / radial bearing side clearance
173: Third partial area of the gap
2: Compressor
20: compressor housing
21: Compressor wheel
22: Filter silencer
3: Axial turbine
30: Turbine housing
31: Turbine wheel
301: gas inlet housing
302: Gas outflow housing
303: Axial extension section of the gas outlet housing
40: first wall protrusion
41: Axial bearing side end face of the discharge face / first wall projection
42: second wall projection
43: Axial bearing side end face of the discharge face / second wall projection
A: Axis of the shaft
F: the face of the first wall projection facing the shaft
F ': the face of the second wall protrusion facing the shaft
50: discharge groove

Claims (9)

A separating device for separating two lubricant streams in a bearing housing (10) of an exhaust gas turbocharger housing a lubricating oil,
A shaft 11 is supported in the exhaust turbo supercharger and the shaft is guided from the turbine housing 30, one side of which is adjacent to the bearing housing, through the bearing housing to the other adjacent side of the compressor housing 20 ,
The exhaust turbo supercharger includes two radial bearings consisting of a turbine side radial bearing 13 and a compressor side radial bearing 12,
The gap 17 and /
And an oil outlet (16) disposed in the region below the compressor-side radial bearing (12) with respect to gravity,
An axial bearing (14) of the shaft is located between the turbine side radial bearing and the compressor side radial bearing,
Said gap being defined by the axially extending portion of said gap being limited by said axial bearing and the other surface being limited by said turbine side bearing and tapering in the direction of said turbine side radial bearing from said radially extending portion of said gap Is limited by the wall section of the bearing housing,
Wherein said oil outlet discharges lubricating oil transferred from said bearing housing by gravity into a clearance region located below said shaft with respect to gravity,
At least one first wall protrusion (40) projecting radially inwardly from the wall of the bearing housing into the gap (17), said first wall protrusion being connected to said turbine Side radial bearing (13), and the side of the first wall projection facing the axial bearing provides a discharge surface (41) for the lubricant conveyed through the axial bearing , The wall projection 40 is formed in such a manner that the clearance 17 is formed at least in a region above the shaft with respect to gravity and in the region 171 adjacent to the axial bearing 14 and the radial bearing 13 on the turbine side And subdivided into adjacent partial regions (172). The method according to claim 1,
Characterized in that said at least one first wall projection (40) surrounds said shaft (11) in the form of a circular ring segment at least in the region of the gap (17) above said shaft in relation to gravity, Characterized in that a radial gap is provided between the shaft surfaces (F). 3. The method of claim 2,
A second wall protrusion (42) formed in the form of a circular segment protrudes radially inward into the gap (17) and the second wall protrusion (42) extends in the axial bearing direction from the first wall protrusion And the surface F 'of the second wall protrusion 42 facing the shaft 11 is offset from the surface F of the first wall protrusion 40 facing the shaft And has a radial distance from the large shaft. The method of claim 3,
The first wall protrusion 40 and / or the second wall protrusion 42 annularly surround the shaft 11 and the annular first side protrusion 40 and / or the annular second protrusion 42, Is not connected to the walls of the bearing housing at least in the area below the shaft (11) with respect to gravity, so that the lubricating oil can penetrate in the area. 5. The method according to any one of claims 1 to 4,
Side radial bearing 13 in order to pass lubricant in the direction of the partial region 172 of the clearance separated from the axial bearing 14 from the space disposed on the turbine side of the turbine side radial bearing 13 Wherein one or more discharge grooves (50) are arranged axially in the wall of the bearing housing, wherein the at least one discharge groove (50) is formed on the turbine side of the turbine side radial bearing (13) And a partial region of the gap is separated from the axial bearing by at least one wall protrusion (40). ≪ Desc / Clms Page number 20 > 6. The method of claim 5,
Wherein two or more discharge grooves (50) are arranged on the turbine side radial bearing (13) in relation to gravity in the partial ring segment of the bearing housing, and the partial ring segment of the bearing housing is arranged on the turbine side radial bearing ) And the two or more discharge grooves are located in an angular range of + 25 ° to + 70 ° or -25 ° to -70 °, as measured from a vertical line. The method according to claim 5 or 6,
Wherein a space on the turbine side of the turbine side radial bearing (13) in the direction of the at least one discharge groove (50) extends radially and axially above the turbine side radial bearing. 8. The method according to any one of claims 1 to 7,
Wherein the discharge surface for lubricating oil conveyed through the axial bearing (14) provided by the side (41) of the at least one wall projection (40) facing the axial bearing is at least partially planarized or coated Wherein the separating device comprises: An exhaust gas turbo supercharger having the separating device according to any one of claims 1 to 8.

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